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  • Inorganic Chemistry  (374)
  • Fluid Mechanics and Thermodynamics
  • 1995-1999  (57)
  • 1990-1994
  • 1950-1954  (378)
  • 1940-1944
  • 1998  (57)
  • 1953  (378)
Collection
Keywords
Publisher
Years
  • 1995-1999  (57)
  • 1990-1994
  • 1950-1954  (378)
  • 1940-1944
Year
  • 1
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    Go With the Flow (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-09
    Description: Under SBIR (Small Business Innovative Research) contracts with Lewis Research Center, Nektonics, Inc., developed coating process simulation tools, known as Nekton. This powerful simulation software is used specifically for the modeling and analysis of a wide range of coating flows including thin film coating analysis, polymer processing, and glass melt flows. Polaroid, Xerox, 3M, Dow Corning, Mead Paper, BASF, Mitsubishi, Chugai, and Dupont Imaging Systems are only a few of the companies that presently use Nekton.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Spinoff 1998; 85; NASA/NP-1998-09-241-HQ
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  • 2
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    Fiber-Supported Droplet Combustion Experiment-2 (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: A major portion of the energy produced in the world today comes from the burning of liquid hydrocarbon fuels in the form of droplets. Understanding the fundamental physical processes involved in droplet combustion is not only important in energy production but also in propulsion, in the mitigation of combustion-generated pollution, and in the control of the fire hazards associated with handling liquid combustibles. Microgravity makes spherically symmetric combustion possible, allowing investigators to easily validate their droplet models without the complicating effects of gravity. The Fiber-Supported Droplet Combustion (FSDC-2) investigation was conducted in the Microgravity Glovebox facility of the shuttles' Spacelab during the reflight of the Microgravity Science Laboratory (MSL- 1R) on STS-94 in July 1997. FSDC-2 studied fundamental phenomena related to liquid fuel droplet combustion in air. Pure fuels and mixtures of fuels were burned as isolated single and duo droplets with and without forced air convection. FSDC-2 is sponsored by the NASA Lewis Research Center, whose researchers are working in cooperation with several investigators from industry and academia. The rate at which a droplet burns is important in many commercial applications. The classical theory of droplet burning assumes that, for an isolated, spherically symmetric, single-fuel droplet, the gas-phase combustion processes are much faster than the droplet surface regression rate and that the liquid phase is at a uniform temperature equal to the boiling point. Recent, more advanced models predict that both the liquid and gas phases are unsteady during a substantial portion of the droplet's burning history, thus affecting the instantaneous and average burning rates, and that flame radiation is a dominant mechanism that can extinguish flames in a microgravity environment. FSDC-2 has provided well-defined, symmetric droplet burning data including radiative emissions to validate these theoretical models for heptane, decane, ethanol, and methanol fuels. Since most commercial combustion systems burn droplets in a convective environment, data were obtained without and with convective flow over the burning droplet (see the following photos).
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 3
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    Overview of Active Flow Control at NASA Langley Research Center (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The paper summarizes Active Flow Control projects currently underway at the NASA Langley Research Center. Technology development is being pursued within a multidisciplinary, cooperative approach, involving the classical disciplines of fluid mechanics, structural mechanics, material science, acoustics, and stability and control theory. Complementing the companion papers in this session, the present paper will focus on projects that have the goal of extending the state-of-the-art in the measurement, prediction, and control of unsteady, nonlinear aerodynamics. Toward this goal, innovative actuators, micro and macro sensors, and control strategies are considered for high payoff flow control applications. The target payoffs are outlined within each section below. Validation of the approaches range from bench-top experiments to wind-tunnel experiments to flight tests. Obtaining correlations for future actuator and sensor designs are implicit in the discussion. The products of the demonstration projects and design tool development from the fundamental NASA R&D level technology will then be transferred to the Applied Research components within NASA, DOD, and US Industry. Keywords: active flow control, separation control, MEMS, review
    Keywords: Fluid Mechanics and Thermodynamics
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  • 4
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    Conceptual Design Method Developed for Advanced Propulsion Nozzles (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: As part of a contract with the NASA Lewis Research Center, a simple, accurate method of predicting the performance characteristics of a nozzle design has been developed for use in conceptual design studies. The Nozzle Performance Analysis Code (NPAC) can predict the on- and off-design performance of axisymmetric or two-dimensional convergent and convergent-divergent nozzle geometries. NPAC accounts for the effects of overexpansion or underexpansion, flow divergence, wall friction, heat transfer, and small mass addition or loss across surfaces when the nozzle gross thrust and gross thrust coefficient are being computed. NPAC can be used to predict the performance of a given nozzle design or to develop a preliminary nozzle system design for subsequent analysis. The input required by NPAC consists of a simple geometry definition of the nozzle surfaces, the location of key nozzle stations (entrance, throat, exit), and the nozzle entrance flow properties. NPAC performs three analysis "passes" on the nozzle geometry. First, an isentropic control volume analysis is performed to determine the gross thrust and gross thrust coefficient of the nozzle. During the second analysis pass, the skin friction and heat transfer losses are computed. The third analysis pass couples the effects of wall shear and heat transfer with the initial internal nozzle flow solutions to produce a system of equations that is solved at steps along the nozzle geometry. Small mass additions or losses, such as those resulting from leakage or bleed flow, can be included in the model at specified geometric sections. A final correction is made to account for divergence losses that are incurred if the nozzle exit flow is not purely axial.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 5
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    On Some Numerical Dissipation Schemes (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Several schemes for introducing an artificial dissipation into a central difference approximation to the Euler and Navier Stokes equations are considered. The focus of the paper is on the convective upwind and split pressure (CUSP) scheme, which is designed to support single interior point discrete shock waves. This scheme is analyzed and compared in detail with scalar dissipation and matrix dissipation (MATD) schemes. Resolution capability is determined by solving subsonic, transonic, and hypersonic flow problems. A finite-volume discretization and a multistage time-stepping scheme with multigrid are used to compute solutions to the flow equations. Numerical solutions are also compared with either theoretical solutions or experimental data. For transonic airfoil flows the best accuracy on coarse meshes for aerodynamic coefficients is obtained with a simple MATD scheme. The coarse-grid accuracy for the original CUSP scheme is improved by modifying the limiter function used with the scheme, giving comparable accuracy to that obtained with the MATD scheme. The modifications reduce the background dissipation and provide control over the regions where the scheme can become first order.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 6
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    Aircraft Laminar Flow Control (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Aircraft laminar flow control (LFC) from the 1930's through the 1990's is reviewed and the current status of the technology is assessed. Examples are provided to demonstrate the benefits of LFC for subsonic and supersonic aircraft. Early studies related to the laminar boundary-layer flow physics, manufacturing tolerances for laminar flow, and insect-contamination avoidance are discussed. LFC concept studies in wind-tunnel and flight experiments are the major focus of the paper. LFC design tools are briefly outlined for completeness.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Annual Review of Fluid Mechanics 1998; Volume 30; 1-29
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  • 7
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    Radiation Heat Transfer Modeling Improved for Phase-Change, Thermal Energy Storage Systems (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Spacecraft solar dynamic power systems typically use high-temperature phase-change materials to efficiently store thermal energy for heat engine operation in orbital eclipse periods. Lithium fluoride salts are particularly well suited for this application because of their high heat of fusion, long-term stability, and appropriate melting point. Considerable attention has been focused on the development of thermal energy storage (TES) canisters that employ either pure lithium fluoride (LiF), with a melting point of 1121 K, or eutectic composition lithium-fluoride/calcium-difluoride (LiF-20CaF2), with a 1040 K melting point, as the phase-change material. Primary goals of TES canister development include maximizing the phase-change material melt fraction, minimizing the canister mass per unit of energy storage, and maximizing the phase-change material thermal charge/discharge rates within the limits posed by the container structure.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 8
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    Mixing of Multiple Jets With a Confined Subsonic Crossflow (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Results from a recently completed enhanced mixing program are summarized in the two technical papers. These studies were parts of a High Speed Research (HSR)-supported joint Government/industry/university program that involved, in addition to the NASA Lewis Research Center, researchers at United Technologies Research Center, Allison Engine Company, CFD Research Corporation, and the University of California, Irvine. The studies investigated the mixing of jets injected normal to a confined subsonic mainsteam in both rectangular and cylindrical ducts. Experimental and computational studies were performed in both nonreacting and reacting flows. The orifice geometries and flow conditions were selected as typical of the complex three-dimensional flows in the combustion chambers in low-emission gas turbine engines. The principal conclusion from both the experiments and modeling was that the momentum-flux ratio J and orifice spacing S/H were the most significant flow and geometry variables, respectively. Conserved scalar distributions were similar-independent of reaction, orifice diameter H/d, and shape-when the orifice spacing and the square root of the momentum-flux ratio were inversely proportional. Jet penetration was critical, and penetration decreased as either momentum-flux ratio or orifice spacing decreased. We found that planar averages must be considered in context with the distributions. The mass-flow ratios and the orifices investigated were often very large. The jet-to-mainstream mass-flow ratio was varied from significantly less than 1 to greater than 1. The orifice-area to mainstream-cross-sectional-area was varied from approx. 0 to 0.5, and the axial planes of interest were often just downstream of the orifice trailing edge. Three-dimensional flow was a key part of efficient mixing and was observed for all configurations. As an example of the results, the accompanying figure shows the effects of different rates of mass addition on the opposite walls of a rectangular duct.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 9
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    Capillary-Driven Heat Transfer Experiment: Keeping It Cool in Space (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Capillary-pumped loops (CPL's) are devices that are used to transport heat from one location to another--specifically to transfer heat away from something. In low-gravity applications, such as satellites (and possibly the International Space Station), CPL's are used to transfer heat from electrical devices to space radiators. This is accomplished by evaporating one liquid surface on the hot side of the CPL and condensing the vapor produced onto another liquid surface on the cold side. Capillary action, the phenomenon that causes paper towels to absorb spilled liquids, is used to "pump" the liquid back to the evaporating liquid surface (hot side) to complete the "loop." CPL's require no power to operate and can transfer heat over distances as large as 30 ft or more. Their reliance upon evaporation and condensation to transfer heat makes them much more economical in terms of weight than conventional heat transfer systems. Unfortunately, they have proven to be unreliable in space operations, and the explanation for this unreliability has been elusive. The Capillary-Driven Heat Transfer (CHT) experiment is investigating the fundamental fluid physics phenomena thought to be responsible for the failure of CPL's in low-gravity operations. If the failure mechanism can be identified, then appropriate design modifications can be developed to make capillary phase-change heat-transport devices a more viable option in space applications. CHT was conducted onboard the Space Shuttle Columbia during the first Microgravity Science Laboratory (MSL-1) mission, STS-94, which flew from July 1 to 17, 1997. The CHT glovebox investigation, which was conceived by Dr. Kevin Hallinan and Jeffrey Allen of the University of Dayton, focused on studying the dynamics associated with the heating and cooling at the evaporating meniscus within a capillary phase-change device in a low-gravity environment. The CHT experimental hardware was designed by a small team of engineers from Aerospace Design & Fabrication (ADF), the NASA Lewis Research Center, and the University of Dayton. The hardware consisted of two experiment modules that each contained an instrumented test loop (idealized capillary-pumped loop), a base unit for power conversion and backlighting, a display unit with 15 LED's (light-emitting diodes) to display temperatures, pressure, heater power, and time, a control unit to select heaters and heater settings, a cooling fan, and associated cables.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 10
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    Thermal Effects Modeling Developed for Smart Structures (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Applying smart materials in aeropropulsion systems may improve the performance of aircraft engines through a variety of vibration, noise, and shape-control applications. To facilitate the experimental characterization of these smart structures, researchers have been focusing on developing analytical models to account for the coupled mechanical, electrical, and thermal response of these materials. One focus of current research efforts has been directed toward incorporating a comprehensive thermal analysis modeling capability. Typically, temperature affects the behavior of smart materials by three distinct mechanisms: Induction of thermal strains because of coefficient of thermal expansion mismatch 1. Pyroelectric effects on the piezoelectric elements; 2. Temperature-dependent changes in material properties; and 3. Previous analytical models only investigated the first two thermal effects mechanisms. However, since the material properties of piezoelectric materials generally vary greatly with temperature (see the graph), incorporating temperature-dependent material properties will significantly affect the structural deflections, sensory voltages, and stresses. Thus, the current analytical model captures thermal effects arising from all three mechanisms through thermopiezoelectric constitutive equations. These constitutive equations were incorporated into a layerwise laminate theory with the inherent capability to model both the active and sensory response of smart structures in thermal environments. Corresponding finite element equations were formulated and implemented for both the beam and plate elements to provide a comprehensive thermal effects modeling capability.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 11
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    Three-Dimensional Measurements of Fuel Distribution in High-Pressure, High- Temperature, Next-Generation Aviation Gas Turbine Combustors (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: In our world-class, optically accessible combustion facility at the NASA Lewis Research Center, we have developed the unique capability of making three-dimensional fuel distribution measurements of aviation gas turbine fuel injectors at actual operating conditions. These measurements are made in situ at the actual operating temperatures and pressures using the JP-grade fuels of candidate next-generation advanced aircraft engines for the High Speed Research (HSR) and Advanced Subsonics Technology (AST) programs. The inlet temperature and pressure ranges used thus far are 300 to 1100 F and 80 to 250 psia. With these data, we can obtain the injector spray angles, the fuel mass distributions of liquid and vapor, the degree of fuel vaporization, and the degree to which fuel has been consumed. The data have been used to diagnose the performance of injectors designed both in-house and by major U.S. engine manufacturers and to design new fuel injectors with overall engine performance goals of increased efficiency and reduced environmental impact. Mie scattering is used to visualize the liquid fuel, and laser-induced fluorescence is used to visualize both liquid and fuel vapor.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 12
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    LSPRAY: Lagrangian Spray Solver for Applications With Parallel Computing and Unstructured Gas-Phase Flow Solvers (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Sprays occur in a wide variety of industrial and power applications and in the processing of materials. A liquid spray is a phase flow with a gas as the continuous phase and a liquid as the dispersed phase (in the form of droplets or ligaments). Interactions between the two phases, which are coupled through exchanges of mass, momentum, and energy, can occur in different ways at different times and locations involving various thermal, mass, and fluid dynamic factors. An understanding of the flow, combustion, and thermal properties of a rapidly vaporizing spray requires careful modeling of the rate-controlling processes associated with the spray's turbulent transport, mixing, chemical kinetics, evaporation, and spreading rates, as well as other phenomena. In an attempt to advance the state-of-the-art in multidimensional numerical methods, we at the NASA Lewis Research Center extended our previous work on sprays to unstructured grids and parallel computing. LSPRAY, which was developed by M.S. Raju of Nyma, Inc., is designed to be massively parallel and could easily be coupled with any existing gas-phase flow and/or Monte Carlo probability density function (PDF) solver. The LSPRAY solver accommodates the use of an unstructured mesh with mixed triangular, quadrilateral, and/or tetrahedral elements in the gas-phase solvers. It is used specifically for fuel sprays within gas turbine combustors, but it has many other uses. The spray model used in LSPRAY provided favorable results when applied to stratified-charge rotary combustion (Wankel) engines and several other confined and unconfined spray flames. The source code will be available with the National Combustion Code (NCC) as a complete package.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 13
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    Liquid-Vapor Interface Configurations Investigated in Low Gravity (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The Interface Configuration Experiment (ICE) is part of a multifaceted study that is exploring the often striking behavior of liquid-vapor interfaces in low-gravity environments. Although the experiment was posed largely as a test of current mathematical theory, applications of the results should be manifold. In space almost every fluid system is affected, if not dominated, by capillarity (the effects of surface tension). As a result, knowledge of fluid interface behavior, in particular an equilibrium interface shape from which any analysis must begin, is fundamental--from the control of liquid fuels and oxygen in storage tanks to the design and development of inspace thermal systems, such as heat pipes and capillary pumped loops. ICE has increased, and should continue to increase, such knowledge as it probes the specific peculiarities of current theory upon which our present understanding rests. Several versions of ICE have been conducted in the drop towers at the NASA Lewis Research Center, on the space shuttles during the first and second United States Microgravity Laboratory missions (USML-1 and USML-2), and most recently aboard the Russian Mir space station. These studies focused on interfacial problems concerning the existence, uniqueness, configuration, stability, and flow characteristics of liquid-vapor interfaces. Results to date have clearly demonstrated the value of the present theory and the extent to which it can predict the behavior of capillary systems.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 14
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    Particle Imaging Velocimetry Used in a Transonic Compressor Facility (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Particle Imaging Velocimetry (PIV) is an optical technique whereby a pulsed laser sheet is used to illuminate particles entrained in a fluid across an extended planar cross section of a flow field. Electronic recording of the particle positions at two closely timed laser pulses permits the computation of the flow velocity. PIV captures the instantaneous flow field, permitting the study of unsteady flow phenomena. Mean flow statistics can be computed by acquiring several hundred images and averaging the results. The first-ever successful application of PIV to acquire measurements in a high-speed rotating turbomachinery blade row was completed in NASA Lewis Research Center's W-8 Single Stage Axial Compressor Facility. Measurements were acquired in a 20-in.-diameter transonic compressor rotor operating at 17,188 rpm. A custom-designed light-sheet generating probe was used to insert the high-energy, pulsed light-sheet illumination required for recording the unblurred images of particles entrained in the fluid. Measurements of the shock wave formed within the rotor blade passage and of unsteady structures within the blade wakes were acquired. These measurements provide insight into unsteady spatial structures in the flow field which cannot be measured with the more conventional laser anemometry technique. The PIV technique provides both instantaneous and average velocity data in a transonic compressor in an order of magnitude less time than required for other conventional optical diagnostic techniques.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 15
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    Thermal High- and Low-Cycle Fatigue Behavior of Thick Thermal Barrier Coating Systems (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Ceramic thermal barrier coatings have received increasing attention for advanced gas turbine and diesel engine applications because of their ability to provide thermal insulation to engine components. However, the durability of these coatings under the severe thermal cycling conditions encountered in a diesel engine (ref. 1) still remains a major issue. In this research at the NASA Lewis Research Center, a high-power laser was used to investigate the thermal fatigue behavior of a yttria-stabilized zirconia coating system under simulated diesel engine conditions. The mechanisms of fatigue crack initiation and propagation, and of coating failure under complex thermal low-cycle fatigue (LCF, representing stop/start cycles) and thermal high-cycle fatigue (HCF, representing operation at 1300 rpm) are described. Continuous wave and pulse laser modes were used to simulate pure LCF and combined LCF/HCF, respectively (ref. 2). The LCF mechanism was found to be closely related to the coating sintering and creep at high temperatures. These creep strains in the ceramic coating led to a tensile stress state during cooling, thus providing the major driving force for crack growth under LCF conditions. The combined LCF/HCF tests induced more severe coating surface cracking, microspallation, and accelerated crack growth than did the pure LCF test. HCF thermal loads also facilitated lateral crack branching and ceramic/bond coat interface delaminations. HCF is associated with the cyclic stresses originating from the high-frequency temperature fluctuation at the ceramic coating surface. The HCF thermal loads act on the crack by a wedging mechanism (ref. 1), resulting in continuous crack growth at temperature. The HCF stress intensity factor amplitude increases with the interaction depth and temperature swing, and decreases with the crack depth. HCF damage also increases with the thermal expansion coefficient and the Young's modulus of the ceramic coating (refs. 1 and 3).
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 16
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    Microblowing Technique Demonstrated to Reduce Skin Friction (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: One of the most challenging areas of research in aerodynamics is the reduction of skin friction, especially for turbulent flow. Reduced skin friction means less drag. For aircraft, less drag can lead to less fuel burned or to a greater flight range for a fixed amount of fuel. Many techniques and methods have been tried; however, none of them has significantly reduced skin friction in the flight environment. An innovative skin-friction reduction technique, the Microblowing Technique (MBT), was invented in 1993. This is a unique concept in which an extremely small amount of air is blown vertically at a surface through very small holes. It can be used for aircraft or marine vehicles, such as submarines (where water is blown through the holes instead of air). As shown in the figure, the outer layer, which controls vertical flow, is a plate with high-vertical holes. The inner layer, which produces evenly distributed flow, is a low-permeability porous plate. Microblowing reduces the surface roughness and changes the flow velocity profile on the surface, thereby reducing skin friction.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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  • 17
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    CGNS Mid-Level Software Library and Users Guide (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The "CFD General Notation System" (CGNS) consists of a collection of conventions, and conforming software, for the storage and retrieval of Computational Fluid Dynamics (CFD) data. It facilitates the exchange of data between sites and applications, and helps stabilize the archiving of aerodynamic data. This effort was initiated in order to streamline the procedures in exchanging data and software between NASA and its customers, but the goal is to develop CGNS into a National Standard for the exchange of aerodynamic data. The CGNS development team is comprised of members from Boeing Commercial Airplane Group, NASA-Ames, NASA-Langley, NASA-Lewis, McDonnell-Douglas Corporation (now Boeing-St. Louis), Air Force-Wright Lab., and ICEM-CFD Engineering. The elements of CGNS address all activities associated with the storage of data on external media and its movement to and from application programs. These elements include: - The Advanced Data Format (ADF) Database manager, consisting of both a file format specification and its I/O software, which handles the actual reading and writing of data from and to external storage media; - The Standard Interface Data Structures (SIDS), which specify the intellectual content of CFD data and the conventions governing naming and terminology; - The SIDS-to-ADF File Mapping conventions, which specify the exact location where the CFD data defined by the SIDS is to be stored within the ADF file(s); and - The CGNS Mid-level Library, which provides CFD-knowledgeable routines suitable for direct installation into application codes. The CGNS Mid-level Library was designed to ease the implementation of CGNS by providing developers with a collection of handy I/O functions. Since knowledge of the ADF core is not required to use this library, it will greatly facilitate the task of interfacing with CGNS. There are currently 48 user callable functions that comprise the Mid-level library and are described in the Users Guide. The library is written in C, but each function has a FORTRAN counterpart.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 18
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    Experimental Study of Lift-Generated Vortices (1998)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: The flow fields of vortices, whether bouyancy-driven or lift-generated, are fascinating fluid-dynamic phenomena which often possess intense swirl velocities and complex time-dependent behavior. As part of the on-going study of vortex behavior, this paper presents a historical overview of the research conducted on the structure and modification of the vortices generated by the lifting surfaces of subsonic transport aircraft. It is pointed out that the characteristics of lift-generated vortices are related to the aerodynamic shapes that produce them and that various arrangements of surfaces can be used to produce different vortex structures. The primary purpose of the research to be described is to find a way to reduce the hazard potential of lift-generated vortices shed by subsonic transport aircraft in the vicinity of airports during landing and takeoff operations. It is stressed that lift-generated vortex wakes are so complex that progress towards a solution requires application of a combined theoretical and experimental research program because either alone often leads to incorrect conclusions. It is concluded that a satisfactory aerodynamic solution to the wake-vortex problem at airports has not yet been found but a reduction in the impact of the wake-vortex hazard on airport capacity may become available in the foreseeable future through wake-vortex avoidance concepts currently under study. The material to be presented in this overview is drawn from aerospace journals that are available publicly.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 19
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    Advanced Data Format (ADF) Software Library and Users Guide (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The "CFD General Notation System" (CGNS) consists of a collection of conventions, and conforming software, for the storage and retrieval of Computational Fluid Dynamics (CFD) data. It facilitates the exchange of data between sites and applications, and helps stabilize the archiving of aerodynamic data. This effort was initiated in order to streamline the procedures in exchanging data and software between NASA and its customers, but the goal is to develop CGNS into a National Standard for the exchange of aerodynamic data. The CGNS development team is comprised of members from Boeing Commercial. Airplane Group, NASA-Ames, NASA-Langley, NASA-Lewis, McDonnell-Douglas Corporation (now Boeing-St. Louis), Air Force-Wright Lab., and ICEM-CFD Engineering. The elements of CGNS address all activities associated with the storage of data on external media and its movement to and from application programs. These elements include: 1) The Advanced Data Format (ADF) Database manager, consisting of both a file format specification and its 1/0 software, which handles the actual reading and writing of data from and to external storage media; 2) The Standard Interface Data Structures (SIDS), which specify the intellectual content of CFD data and the conventions governing naming and terminology; 3) The SIDS-to-ADF File Mapping conventions, which specify the exact location where the CFD data defined by the SIDS is to be stored within the ADF file(s); and 4) The CGNS Mid-level Library, which provides CFD-knowledgeable routines suitable for direct installation into application codes. The ADF is a generic database manager with minimal intrinsic capability. It was written for the purpose of storing large numerical datasets in an efficient, platform independent manner. To be effective, it must be used in conjunction with external agreements on how the data will be organized within the ADF database such defined by the SIDS. There are currently 34 user callable functions that comprise the ADF Core library and are described in the Users Guide. The library is written in C, but each function has a FORTRAN counterpart.
    Keywords: Fluid Mechanics and Thermodynamics
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    Experimental and Computational Boundary-Layer Studies In a Supersonic Two-Dimensional Nozzle (1998)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: Experiments and computations were carried out on the adiabatic laminar boundary layer developing along the surfaces of a two-dimensional supersonic nozzle, consisting of upper and lower contoured nozzle blocks and flat sidewalls. Two- and three-dimensional Navier-Stokes codes, as well as two-dimensional boundary-layer codes were employed. These codes were adapted to the characteristics of a specific wind tunnel nozzle, so that their numerical results could be directly compared with experimental data obtained in the same nozzle. Such comparisons were made for the boundary-layer growth on the nozzle contoured surfaces, and for the boundary-layer growth, surface streamlines and surface shear on the sidewalls. The three-dimensional Navier-Stokes code was found to be the only one to correctly predict the mean laminar boundary-layer flow on both the sidewalls and the contoured surfaces. Theory and experiment both indicated that the sidewall flow is highly three-dimensional, with non-uniform shear, corner vortices and a boundary layer strongly distorted by cross flows induced by lateral pressure gradients.
    Keywords: Fluid Mechanics and Thermodynamics
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    Executive Summary: Special Section on Credible Computational Fluid Dynamics Simulations (1998)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: This summary presents the motivation for the Special Section on the credibility of computational fluid dynamics (CFD) simulations, its objective, its background and context, its content, and its major conclusions. Verification and validation (V&V) are the processes for establishing the credibility of CFD simulations. Validation assesses whether correct things are performed and verification assesses whether they are performed correctly. Various aspects of V&V are discussed. Progress is made in verification of simulation models. Considerable effort is still needed for developing a systematic validation method that can assess the credibility of simulated reality.
    Keywords: Fluid Mechanics and Thermodynamics
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    Workload Characterization of CFD Applications Using Partial Differential Equation Solvers (1998)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: Workload characterization is used for modeling and evaluating of computing systems at different levels of detail. We present workload characterization for a class of Computational Fluid Dynamics (CFD) applications that solve Partial Differential Equations (PDEs). This workload characterization focuses on three high performance computing platforms: SGI Origin2000, EBM SP-2, a cluster of Intel Pentium Pro bases PCs. We execute extensive measurement-based experiments on these platforms to gather statistics of system resource usage, which results in workload characterization. Our workload characterization approach yields a coarse-grain resource utilization behavior that is being applied for performance modeling and evaluation of distributed high performance metacomputing systems. In addition, this study enhances our understanding of interactions between PDE solver workloads and high performance computing platforms and is useful for tuning these applications.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Workshop on Workload Characterization in High Performance Computing Environments; Jul 19, 1998 - Jul 24, 1998; Montreal; Canada
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    Tetrahedral Finite-Volume Solutions to the Navier-Stokes Equations on Complex Configurations (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: A review of the algorithmic features and capabilities of the unstructured-grid flow solver USM3Dns is presented. This code, along with the tetrahedral grid generator, VGRIDns, is being extensively used throughout the U.S. for solving the Euler and Navier-Stokes equations on complex aerodynamic problems. Spatial discretization is accomplished by a tetrahedral cell-centered finite-volume formulation using Roe's upwind flux difference splitting. The fluxes are limited by either a Superbee or MinMod limiter. Solution reconstruction within the tetrahedral cells is accomplished with a simple, but novel, multidimensional analytical formula. Time is advanced by an implicit backward-Euler time-stepping scheme. Flow turbulence effects are modeled by the Spalart-Allmaras one-equation model, which is coupled with a wall function to reduce the number of cells in the near-wall region of the boundary layer. The issues of accuracy and robustness of USM3Dns Navier-Stokes capabilities are addressed for a flat-plate boundary layer, and a full F-16 aircraft with external stores at transonic speed.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Tenth International Conference on Finite Elements in Fluids; Jan 05, 1998 - Jan 08, 1998; Tucson, AZ; United States
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    The Application of Nonstandard Analysis to the Study of Inviscid Shock Wave Jump Conditions (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The use of conservation laws in nonconservative form for deriving shock jump conditions by Schwartz distribution theory leads to ambiguous products of generalized functions. Nonstandard analysis is used to define a class of Heaviside functions where the jump from zero to one occurs on an infinitesimal interval. These Heaviside functions differ by their microstructure near x = 0, i.e., by the nature of the rise within the infinitesimal interval it is shown that the conservation laws in nonconservative form can relate the different Heaviside functions used to define jumps in different flow parameters. There are no mathematical or logical ambiguities in the derivation of the jump conditions. An important result is that the microstructure of the Heaviside function of the jump in entropy has a positive peak greater than one within the infinitesimal interval where the jump occurs. This phenomena is known from more sophisticated studies of the structure of shock waves using viscous fluid assumption. However, the present analysis is simpler and more direct.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: 51st Annual Meeting of APS Division of Fluid Mechanics; Nov 22, 1998 - Nov 24, 1998; Philadelphia, PA; United States
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    PAB3D Simulations of a Nozzle with Fluidic Injection for Yaw Thrust-Vector Control (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: An experimental and computational study was conducted on an exhaust nozzle with fluidic injection for yaw thrust-vector control. The nozzle concept was tested experimentally in the NASA Langley Jet Exit Test Facility (JETF) at nozzle pressure ratios up to 4 and secondary fluidic injection flow rates up to 15 percent of the primary flow rate. Although many injection-port geometries and two nozzle planforms (symmetric and asymmetric) were tested experimentally, this paper focuses on the computational results of the more successful asymmetric planform with a slot injection port. This nozzle concept was simulated with the Navier-Stokes flow solver, PAB3D, invoking the Shih, Zhu, and Lumley algebraic Reynolds stress turbulence model (ASM) at nozzle pressure ratios (NPRs) of 2,3, and 4 with secondary to primary injection flow rates (w(sub s)/w(sub p)) of 0, 2, 7 and 10 percent.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-3254 , 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 13, 1998 - Jul 15, 1998; Cleveland, OH; United States
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    The Use of Heavy Gas for Increased Reynolds Numbers in Transonic Wind Tunnels (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The use of a high molecular weight test gas to increase the Reynolds number range of transonic wind tunnels is explored. Modifications to a small transonic wind tunnel are described and the real gas properties of the example heavy gas (sulfur hexafluoride) are discussed. Sulfur hexafluoride is shown to increase the test Reynolds number by a factor of more than 2 over air at the same Mach number. Experimental and computational pressure distributions on an advanced supercritical airfoil configuration at Mach 0.7 in both sulfur hexafluoride and nitrogen are presented. Transonic similarity theory is shown to be partially successful in transforming the heavy gas results to equivalent nitrogen (air) results, provided the correct definition of gamma is used.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-2882 , 20th AIAA Advanced Measurement and Ground Testing Technology Conference; Jun 15, 1998 - Jun 18, 1998; Albuquerque, NN; United States
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    Grid Generation Techniques Utilizing the Volume Grid Manipulator (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: This paper presents grid generation techniques available in the Volume Grid Manipulation (VGM) code. The VGM code is designed to manipulate existing line, surface and volume grids to improve the quality of the data. It embodies an easy to read rich language of commands that enables such alterations as topology changes, grid adaption and smoothing. Additionally, the VGM code can be used to construct simplified straight lines, splines, and conic sections which are common curves used in the generation and manipulation of points, lines, surfaces and volumes (i.e., grid data). These simple geometric curves are essential in the construction of domain discretizations for computational fluid dynamic simulations. By comparison to previously established methods of generating these curves interactively, the VGM code provides control of slope continuity and grid point-to-point stretchings as well as quick changes in the controlling parameters. The VGM code offers the capability to couple the generation of these geometries with an extensive manipulation methodology in a scripting language. The scripting language allows parametric studies of a vehicle geometry to be efficiently performed to evaluate favorable trends in the design process. As examples of the powerful capabilities of the VGM code, a wake flow field domain will be appended to an existing X33 Venturestar volume grid; negative volumes resulting from grid expansions to enable flow field capture on a simple geometry, will be corrected; and geometrical changes to a vehicle component of the X33 Venturestar will be shown.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-3012 , 29th AIAA Fluid Dynamics Conference; Jun 15, 1998 - Jun 18, 1998; Albuquerque, NM; United States
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    Heavy Gas Conversion of the NASA Langley Transonic Dynamics Tunnel (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The heavy gas test medium has recently been changed in the Transonic Dynamics Tunnel (TDT) at the NASA Langley Research Center. A NASA Construction of Facilities project has converted the TDT heavy gas from dichlorodifluoromethane (R12) to 1,1,1,2 tetrafluoroethane (R134a). The facility s heavy gas processing system was extensively modified to implement the conversion to R134a. Additional system modifications have improved operator interfaces, hardware reliability, and quality of the research data. The facility modifications included improvements to the heavy gas compressor and piping, the cryogenic heavy gas reclamation system, and the heavy gas control room. A series of wind tunnel characterization and calibration tests are underway. Results of the flow characterization tests show the TDT operating envelope in R134a to be very similar to the previous operating envelope in R12.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-2710 , 20th AIAA Advanced Measurement and Ground Testing Technology Conference; Jun 15, 1998 - Jun 18, 1998; Albuquerque, NM; United States
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    Reduction and Analysis of Phosphor Thermography Data With the IHEAT Software Package (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Detailed aeroheating information is critical to the successful design of a thermal protection system (TPS) for an aerospace vehicle. This report describes NASA Langley Research Center's (LaRC) two-color relative-intensity phosphor thermography method and the IHEAT software package which is used for the efficient data reduction and analysis of the phosphor image data. Development of theory is provided for a new weighted two-color relative-intensity fluorescence theory for quantitatively determining surface temperatures on hypersonic wind tunnel models; an improved application of the one-dimensional conduction theory for use in determining global heating mappings; and extrapolation of wind tunnel data to flight surface temperatures. The phosphor methodology at LaRC is presented including descriptions of phosphor model fabrication, test facilities and phosphor video acquisition systems. A discussion of the calibration procedures, data reduction and data analysis is given. Estimates of the total uncertainties (with a 95% confidence level) associated with the phosphor technique are shown to be approximately 8 to 10 percent in the Langley's 31-Inch Mach 10 Tunnel and 7 to 10 percent in the 20-Inch Mach 6 Tunnel. A comparison with thin-film measurements using two-inch radius hemispheres shows the phosphor data to be within 7 percent of thin-film measurements and to agree even better with predictions via a LATCH computational fluid dynamics solution (CFD). Good agreement between phosphor data and LAURA CFD computations on the forebody of a vertical takeoff/vertical lander configuration at four angles of attack is also shown. In addition, a comparison is given between Mach 6 phosphor data and laminar and turbulent solutions generated using the LAURA, GASP and LATCH CFD codes. Finally, the extrapolation method developed in this report is applied to the X-34 configuration with good agreement between the phosphor extrapolation and LAURA flight surface temperature predictions. The phosphor process outlined in the paper is believed to provide the aerothermodynamic community with a valuable capability for rapidly obtaining (4 to 5 weeks) detailed heating information needed in TPS design.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-0712 , 36th AIAA Aerospace Sciences Meeting and Exhibit; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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    Taking the Heat Off Thermal Loads (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Under an SBIR (Small Business Innovative Research) contract with Goddard Space Flight Center, (NAS5-32730), Frederick A. Costello, Inc., has developed a low cost computer program for integrating thermal modeling with other engineering disciplines. TCON(tm) Concurrent Engineering Software enables graphical user-interface programs to create three dimensional models. This technology reduces time, and facilitates accuracy while performing these applications. TCON(tm) has been sold to NASA and major US industries.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Spinoff 1998; 84; NASA/NP-1998-09-241-HQ
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    Evaluation of Aeroservoelastic Effects on Flutter (1998)
    In:  CASI
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    Publication Date: 2019-07-12
    Description: This report presents work performed by The Boeing Company to satisfy the deliverable "Evaluation of aeroservoelastic Effects on Symmetric Flutter" for Subtask 7 of Reference 1. The objective of this report is to incorporate the improved methods for studying the effects of a closed-loop control system on the aeroservoelastic behavior of the airplane planned under NASA HSR technical Integration Task 20 work. Also, a preliminary evaluation of the existing pitch control laws on symmetric flutter of the TCA configuration was addressed."The goal is to develop an improved modeling methodology and perform design studies that account for the aero-structures-systems interaction effects.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NF1676L-13588
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    Preliminary Evaluation of Nonlinear Effects on TCA Flutter (1998)
    In:  CASI
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    Publication Date: 2019-07-12
    Description: The objective of this study is to investigate the effect of nonlinear aerodynamics, especially at high angles-of-attack with leading-edge separation, on the TCA flutter properties at transonic speeds. In order to achieve that objective, flutter simulations with Navier-Stokes CFD must be performed. To this end, time-marching Navier-Stokes solutions are computed for the TCA wing/body configuration at high angles-of-attack in transonic flight regimes. The approach is to perform non-linear flutter calculations on the TCA at two angles-of-attack, the first one being a case with attached flow (a=2.8 degrees) and the second one being a high angle-of-attack case with a wing leading edge vortex (a=12.11 degrees). Comparisons of the resulting histories and frequency damping information for both angles-of-attack will evaluate the impact of high-alpha aerodynamics on flutter.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: CRAD-9408-TR-3027 , NF1676L-13587
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    3D Simulations of the Richtmyer-Meshkov Instability with Re-Shock (1998)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: We present results of inviscid simulations, in three dimensions, of Richtmyer-Meshkov instability for high incident shock Mach number. The growth rate of a single harmonic perturbation is quantified and compared with the results of a 2D calculation. Upon re-shock, the perturbation amplitude undergoes a phase reversal while the mean velocity of the interface is zero. Before re-shock the normalized growth rate of a 2D and 3D interface are nearly the same, but the growth rate after re-shock is significantly larger for the 3D than the 2D case. We also examine the evolution of multiple harmonic perturbations. Computational and parallelization issues of the simulation code will also be briefly discussed. The computations were done on the T3E at Pittsburgh Supercomputing Center.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: American Physical Society, Division of Fluid Dynamics Conference; Nov 22, 1998 - Nov 24, 1998; Philadelphia, PA; United States
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    Recent NASA Wake-Vortex Flight Tests, Flow-Physics Database and Wake-Development Analysis (1998)
    In:  CASI
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    Publication Date: 2019-07-10
    Description: A series of flight tests over the ocean of a four engine turboprop airplane in the cruise configuration have provided a data set for improved understanding of wake vortex physics and atmospheric interaction. An integrated database has been compiled for wake characterization and validation of wake-vortex computational models. This paper describes the wake-vortex flight tests, the data processing, the database development and access, and results obtained from preliminary wake-characterization analysis using the data sets.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Rept-985592
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    Flow analysis system and method (1998)
    In:  CASI
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    Publication Date: 2019-07-12
    Description: A non-invasive flow analysis system and method wherein a sensor, such as an acoustic sensor, is coupled to a conduit for transmitting a signal which varies depending on the characteristics of the flow in the conduit. The signal is amplified and there is a filter, responsive to the sensor signal, and tuned to pass a narrow band of frequencies proximate the resonant frequency of the sensor. A demodulator generates an amplitude envelope of the filtered signal and a number of flow indicator quantities are calculated based on variations in amplitude of the amplitude envelope. A neural network, or its equivalent, is then used to determine the flow rate of the flow in the conduit based on the flow indicator quantities.
    Keywords: Fluid Mechanics and Thermodynamics
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    Multipoint Measurements in an Axisymmetric Sudden Expansion (1998)
    In:  CASI
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    Publication Date: 2019-08-15
    Description: A flying wire system was utilized in conjunction with a rake of nine cross-wire probes to obtain simultaneous velocity measurements in an axisymmetric sudden expansion at a Reynolds number of 41,000. From these measurements, the correlation tensor could be calculated. Knowledge of the two-point correlation tensor reveals more in-depth information of the physical attributes of this flow. The two point correlation tensor allowed for calculation of the integrated length scales in both the radial and axial directions. This gives insight into the growth of structures with increasing downstream distance and at different radial locations through out the sudden expansion. The length scales were calculated by integrating the two-point correlation tensor in the radial direction from the centerline to the outer pipe wall and by integrating between several step heights for the axial direction. Calculated correlations at z/h = 8 and 9 at r/R = 0.46 showed a correlation length of 1/3 step height for the radial direction. It was found that length scales in the radial direction became larger with increasing radius with peaks at 0.70 e r/R c 0.81 but then decreased slightly towards the wall. Length scales in the axial direction yielded a recirculating bubble on the order of 3 step heights in the recirculating region. After the recirculating region, the length scales decreased to 1/4 of a step height.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA University Research Centers Technical Advances in Aeronautics, Space Sciences and Technology, Earth Systems Sciences, Global Hydrology, and Education; s 2 and 3; 954-957; NONP-NASA-CD-1999011585
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    Computational Analysis of a Laminar Jet in a Cross-Flow (1998)
    In:  CASI
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    Publication Date: 2019-08-15
    Description: A jet in cross-flow (JIFC) consists of a jet exhausting at a large angle into a freestream flow. It is a flow field which is relevant to a wide variety of technologies and applications. Despite the nearly 65 years of JIFC research there are few results available for laminar hypersonic flows, a combination which will be encountered by re-entry and high altitude vehicles over some portion of their flight path. This research consists of developing a numerical model to investigate the interaction of a normal sonic jet exhausting into a hypersonic cross-flow. The model was validated by comparing experimental measurements with corresponding numerical results generated by the model.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA University Research Centers Technical Advances in Aeronautics, Space Sciences and Technology, Earth Systems Sciences, Global Hydrology, and Education; 2 and 3; 177-181; NONP-NASA-CD-1999011585
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    Discretization and Preconditioning Algorithms for the Euler and Navier-Stokes Equations on Unstructured Meshes (1998)
    In:  CASI
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    Publication Date: 2019-07-10
    Description: Chapter 1 briefly reviews several related topics associated with the symmetrization of systems of conservation laws and quasi-conservation laws: (1) Basic Entropy Symmetrization Theory; (2) Symmetrization and eigenvector scaling; (3) Symmetrization of the compressible Navier-Stokes equations; and (4) Symmetrization of the quasi-conservative form of the magnetohydrodynamic (MHD) equations. Chapter 2 describes one of the best known tools employed in the study of differential equations, the maximum principle: any function f(x) which satisfies the inequality f(double prime)〉0 on the interval [a,b] attains its maximum value at one of the endpoints on the interval. Chapter three examines the upwind finite volume schemes for scalar and system conservation laws. The basic tasks in the upwind finite volume approach have already been presented: reconstruction, flux evaluation, and evolution. By far, the most difficult task in this process is the reconstruction step.
    Keywords: Fluid Mechanics and Thermodynamics
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    Capillary pumped loop body heat exchanger (1998)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: A capillary pumped loop for transferring heat from one body part to another body part, the capillary pumped loop comprising a capillary evaporator for vaporizing a liquid refrigerant by absorbing heat from a warm body part, a condenser for turning a vaporized refrigerant into a liquid by transferring heat from the vaporized liquid to a cool body part, a first tube section connecting an output port of the capillary evaporator to an input of the condenser, and a second tube section connecting an output of the condenser to an input port of the capillary evaporator. A wick may be provided within the condenser. A pump may be provided between the second tube section and the input port of the capillary evaporator. Additionally, an esternal heat source or heat sink may be utilized.
    Keywords: Fluid Mechanics and Thermodynamics
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    Langley Aerothermodynamic Facilities Complex: Enhancements and Testing Capabilities (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Description, capabilities, recent upgrades, and utilization of the NASA Langley Research Center (LaRC) Aerothermodynamic Facilities Complex (AFC) are presented. The AFC consists of five hypersonic, blow-down-to-vacuum wind tunnels that collectively provide a range of Mach number from 6 to 20, unit Reynolds number from 0.04 to 22 million per foot and, most importantly for blunt configurations, normal shock density ratio from 4 to 12. These wide ranges of hypersonic simulation parameters are due, in part, to the use of three different test gases (air, helium, and tetrafluoromethane), thereby making several of the facilities unique. The Complex represents nearly three-fourths of the conventional (as opposed to impulse)-type hypersonic wind tunnels operational in this country. AFC facilities are used to assess and optimize the hypersonic aerodynamic performance and aeroheating characteristics of aerospace vehicle concepts and to provide benchmark aerodynamic/aeroheating data fr generating the flight aerodynamic databook and final design of the thermal protection system (TPS) (e.g., establishment of flight limitations not to exceed TPS design limits). Modifications and enhancements of AFC hardware components and instrumentation have been pursued to increase capability, reliability, and productivity in support of programmatic goals. Examples illustrating facility utilization in recent years to generate essentially all of the experimental hypersonic aerodynamic and aeroheating information for high-priority, fast-paced Agency programs are presented. These programs include Phase I of the Reusable Launch Vehicle (RLV) Advanced Technology Demonstrator, X-33 program, PHase II of the X-33 program, X-34 program, the Hyper-X program ( a Mach 5,7, and 10 airbreathing propulsion flight experiment), and the X-38 program (Experimental Crew Return Vehicle, X-CRV). Current upgrades/enchancements and future plans for the AFC are discussed.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-0147 , 36th AIAA Aerospace Sciences Meeting and Exhibit; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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    Generation of an Aerothermal Data Base for the X33 Spacecraft (1998)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The X-33 experimental program is a cooperative program between industry and NASA, managed by Lockheed-Martin Skunk Works to develop an experimental vehicle to demonstrate new technologies for a single-stage-to-orbit, fully reusable launch vehicle (RLV). One of the new technologies to be demonstrated is an advanced Thermal Protection System (TPS) being designed by BF Goodrich (formerly Rohr, Inc.) with support from NASA. The calculation of an aerothermal database is crucial to identifying the critical design environment data for the TPS. The NASA Ames X-33 team has generated such a database using Computational Fluid Dynamics (CFD) analyses, engineering analysis methods and various programs to compare and interpolate the results from the CFD and the engineering analyses. This database, along with a program used to query the database, is used extensively by several X-33 team members to help them in designing the X-33. This paper will describe the methods used to generate this database, the program used to query the database, and will show some of the aerothermal analysis results for the X-33 aircraft.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: 1998 National Society of Womens Engineering Convention; Jun 16, 1998 - Jun 20, 1998; Houston, TX; United States
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    Shear-Sensitive Liquid Crystal Coating Method: Surface-Inclination Effects on Shear Vector Measurements (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The shear-sensitive liquid crystal coating (SSLCC) method is an image-based technique for both visualizing dynamic surface-flow phenomena, such as transition and separation, and for measuring the continuous shear-stress vector distribution acting on an aerodynamic surface. Under proper lighting and viewing conditions (discussed below), the coating changes color in response to an applied aerodynamic shear. This color-change response is continuous and reversible, with a response time of milliseconds, and is a function of both the shear magnitude and the shear vector orientation relative to the observer. The liquid crystal phase of matter is a weakly-ordered, viscous, non-Newtonian fluid state that exists between the nonuniform liquid phase and the ordered solid phase of certain organic compounds. Cholesteric liquid crystal compounds possess a helical molecular arrangement that selectively scatters white light, incident along the helical axis, as a three-dimensional spectrum. This property is linked to the helical pitch length, which is within the range of wavelengths in the visible spectrum. The pitch length, and hence the wavelength of the scattered light, is influenced by shear stress normal to the helical axis. This unique optical property produces a measurable color change in response to an applied shearing force. The full-surface shear stress vector measurement method, developed at NASA-Ames, is schematically illustrated. As with the visualization method, the coated test surface is illuminated from the normal direction with white light and the camera is positioned at an above-plane view angle of approximately 30 deg. Experiments have been initiated at NASA Ames to begin the process of quantifying surface-inclination (surface-curvature) effects on shear vector measurement accuracy. In preliminary experiments, surface-inclination angles theta(sub x), theta(sub y) of 0, +/-5, +/-10, and +/-15 deg were employed. In this arrangement, white-light illumination was positioned normal to the untilted test surface, and the camera above-plane view angle was set at 30 deg relative to the untilted test surface. As can be seen, vector-aligned lambda(sub d) values showed no dependence on theta(sub x) or theta(sub y) for absolute values of these tilt angles is less than or equal to 15 deg. Acquisition and analyses of full-surface color images are presently underway to definitively document the insensitivity limits of the shear vector measurement methodology to surface-slope variations.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: 18th International Congress on Instrumentation in Aerospace Simulation Facilities; Jun 21, 1999 - Jun 24, 1999; Toulouse; France
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    Asymptotic Spreading Rate of Initially Compressible Jets-Experiment and Analysis (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Experimental results for the spreading and centerline velocity decay rates for round, compressible jets, from a convergent and a convergent-divergent nozzle, are presented. The spreading rate is determined from the variation of streamwise mass flux obtained from Pitot probe surveys. Results for the far asymptotic region show that both spreading and centerline velocity decay rates, when nondimensionalized by parameters at the nozzle exit, decrease with increasing "jet Mach number" M(sub j). Dimensional analysis with the assumption of momentum conservation, together with compressible flow calculations for the conditions at the nozzle exit, predict this Mach number dependence well. The analysis also demonstrates that an increase in the "potential core length" of the jet occurring with increasing M(sub j), a commonly observed trend, is largely accounted for simply by the variations in the density and static pressure at the nozzle exit. The effect of decreasing mixing efficiency with increasing compressibility is inferred to contribute only partially to the latter trend.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Physics of Fluids; 10; 10; 2652-2660
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    Advanced Methods for Acoustic and Thrust Benefits for Aircraft Engine Nozzle (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose of this paper is to address the problems of Aircraft Engine Technology, Airframe Technology, and Rotorcraft Technology. In addition, several applied problems for domestic industry are also studied using knowledge and experience from Aerospace Sciences. The reduction of aircraft noise is a significant driver in the success of the NASA AST and HSR programs as they attempt to meet stringent international environment regulations on noise for commercial aircraft. In accordance with the project fulfillment under this NASA grant the (Fluid Mechanics and Acoustics Laboratory) FM&AL investigates novel and promising concepts for reduction of noise and improvement of propulsion efficiency in jet exhaust nozzles and fans.
    Keywords: Fluid Mechanics and Thermodynamics
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    Characterization of Asymptotic Entrainment Rate for Compressible Jets (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experimental results for the spreading and centerline velocity decay rates are presented for round, compressible, submerged jets, with total temperature same as ambient temperature, covering a 'jet Mach number' (M(sub J)) range of 0.3 - 2.0. Data from a convergent and a convergent-divergent nozzle are considered. The spreading rate is determined from the total longitudinal mass fluxes measured by Pilot probe survey. Results for the far asymptotic regions show that both spreading and centerline velocity decay rates, when normalized by conditions at the nozzle exit, decrease with increasing M(sub J). Dimensional analysis and isentropic calculations predict this Mach number dependence well. The analysis also demonstrates that an increase in the 'potential core length' of the jet occurring with increasing M(sub J), a commonly observed trend, is largely accounted for simply by the variations in the density and static pressure at the nozzle exit. The effect of decreasing mixing efficiency with increasing compressibility is inferred to contribute only partially to the latter trend.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-0694 , Aerospace Sciences; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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    Numerical Study of Tip Vortex Flows (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents an overview and summary of the many different research work related to tip vortex flows and wake/trailing vortices as applied to practical engineering problems. As a literature survey paper, it outlines relevant analytical, theoretical, experimental and computational study found in literature. It also discusses in brief some of the fundamental aspects of the physics and its complexities. An appendix is also included. The topics included in this paper are: 1) Analytical Vortices; 2) Experimental Studies; 3) Computational Studies; 4) Wake Vortex Control and Management; 5) Wake Modeling; 6) High-Lift Systems; 7) Issues in Numerical Studies; 8) Instabilities; 9) Related Topics; 10) Visualization Tools for Vertical Flows; 11) Further Work Needed; 12) Acknowledgements; 13) References; and 14) Appendix.
    Keywords: Fluid Mechanics and Thermodynamics
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    Prediction of Very High Reynolds Number Compressible Skin Friction (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Flat plate skin friction calculations over a range of Mach numbers from 0.4 to 3.5 at Reynolds numbers from 16 million to 492 million using a Navier Stokes method with advanced turbulence modeling are compared with incompressible skin friction coefficient correlations. The semi-empirical correlation theories of van Driest; Cope; Winkler and Cha; and Sommer and Short T' are used to transform the predicted skin friction coefficients of solutions using two algebraic Reynolds stress turbulence models in the Navier-Stokes method PAB3D. In general, the predicted skin friction coefficients scaled well with each reference temperature theory though, overall the theory by Sommer and Short appeared to best collapse the predicted coefficients. At the lower Reynolds number 3 to 30 million, both the Girimaji and Shih, Zhu and Lumley turbulence models predicted skin-friction coefficients within 2% of the semi-empirical correlation skin friction coefficients. At the higher Reynolds numbers of 100 to 500 million, the turbulence models by Shih, Zhu and Lumley and Girimaji predicted coefficients that were 6% less and 10% greater, respectively, than the semi-empirical coefficients.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 98-2880
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    Automatic Generation of CFD-Ready Surface Triangulations from CAD Geometry (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This paper presents an approach for the generation of closed manifold surface triangulations from CAD geometry. CAD parts and assemblies are used in their native format, without translation, and a part's native geometry engine is accessed through a modeler-independent application programming interface (API). In seeking a robust and fully automated procedure, the algorithm is based on a new physical space manifold triangulation technique which was developed to avoid robustness issues associated with poorly conditioned mappings. In addition, this approach avoids the usual ambiguities associated with floating-point predicate evaluation on constructed coordinate geometry in a mapped space, The technique is incremental, so that each new site improves the triangulation by some well defined quality measure. Sites are inserted using a variety of priority queues to ensure that new insertions will address the worst triangles first, As a result of this strategy, the algorithm will return its 'best' mesh for a given (prespecified) number of sites. Alternatively, the algorithm may be allowed to terminate naturally after achieving a prespecified measure of mesh quality. The resulting triangulations are 'CFD-ready' in that: (1) Edges match the underlying part model to within a specified tolerance. (2) Triangles on disjoint surfaces in close proximity have matching length-scales. (3) The algorithm produces a triangulation such that no angle is less than a given angle bound, alpha, or greater than Pi - 2alpha This result also sets bounds on the maximum vertex degree, triangle aspect-ratio and maximum stretching rate for the triangulation. In addition to tile output triangulations for a variety of CAD parts, tile discussion presents related theoretical results which assert the existence of such all angle bound, and demonstrate that maximum bounds of between 25 deg and 30 deg may be achieved in practice.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 99-0776 , 37th AIAA Aerospace Sciences Meeting; United States
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    Attachment-Line Transition Due to Roughness on a 76 Degree Swept Cylinder at Mach 1.6 (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Experiments were conducted on a 76 deg. swept cylinder to establish the conditions for the attachment-line transition process with, and without, surface roughness in a low-disturbance ("quiet"), Mach number 1.6 flow. Local flow parameters were estimated from pressure measurements. These were in good agreement with predictions from an Euler code (CFL3D) and a boundary layer code (BL3D). Hot-wires and Schlieren photography were used to determine the state of the boundary layer. It was found that, for a near-adiabatic wall condition and a smooth surface, the attachment-line, boundary-layer remained laminar up to the highest attainable Reynolds number (R-bar of 790). Transition under the influence of trip wires was found to depend on wind-tunnel disturbance levels and the onset conditions have been established. Results suggest that current design practice, which is based upon data from conventional ("noisy") tunnels, may be highly conservative.
    Keywords: Fluid Mechanics and Thermodynamics
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    3D Navier-Stokes Time Accurate Solutions Using Multipartitioning Parallel Computation Methodology (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A parallel CFD code solving 3D time accurate Navier-Stokes equations with multipartitioning parallel Methodology is being developed in collaboration with Ohio State University within the Air Vehicle Directorate, at Wright Patterson Air Force Base. The advantage of the multipartitioning parallel method is that the domain decomposition will not introduce domain boundaries for the implicit operators. A ring structure data communication is employed so that the implicit time accurate method can be implemented for multi-processors with the same accuracy as for the single processor. No sub-iteration is needed at the domain boundaries. The code has been validated for some typical unsteady flows, which include Coutte Flow, flow passing a cylinder. The code now is being employed for a large scale time accurate wall jet transient flow computation. 'ne preliminary results are promising. The mesh has been refined to capture more details of the flow field. The mesh refinement computation is in progress and would be difficult to successfully implement without the parallel computation techniques used. A modified version of the code with more efficient inversion of the diagonalized block matrix is currently being tested.
    Keywords: Fluid Mechanics and Thermodynamics
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    Current Status on the use of Parallel Computing in Turbulent Reacting Flow Computations Involving Sprays, Monte Carlo PDF and Unstructured Grids (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The state of the art in multidimensional combustor modeling as evidenced by the level of sophistication employed in terms of modeling and numerical accuracy considerations, is also dictated by the available computer memory and turnaround times afforded by present-day computers. With the aim of advancing the current multi-dimensional computational tools used in the design of advanced technology combustors, a solution procedure is developed that combines the novelty of the coupled CFD/spray/scalar Monte Carlo PDF (Probability Density Function) computations on unstructured grids with the ability to run on parallel architectures. In this approach, the mean gas-phase velocity and turbulence fields are determined from a standard turbulence model, the joint composition of species and enthalpy from the solution of a modeled PDF transport equation, and a Lagrangian-based dilute spray model is used for the liquid-phase representation. The gas-turbine combustor flows are often characterized by a complex interaction between various physical processes associated with the interaction between the liquid and gas phases, droplet vaporization, turbulent mixing, heat release associated with chemical kinetics, radiative heat transfer associated with highly absorbing and radiating species, among others. The rate controlling processes often interact with each other at various disparate time 1 and length scales. In particular, turbulence plays an important role in determining the rates of mass and heat transfer, chemical reactions, and liquid phase evaporation in many practical combustion devices.
    Keywords: Fluid Mechanics and Thermodynamics
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    Pump, and earth-testable spacecraft capillary heat transport loop using augmentation pump and check valves (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A spacecraft includes heat-generating payload equipment, and a heat transport system with a cold plate thermally coupled to the equipment and a capillary-wick evaporator, for evaporating coolant liquid to cool the equipment. The coolant vapor is coupled to a condenser and in a loop back to the evaporator. A heated coolant reservoir is coupled to the loop for pressure control. If the wick is not wetted, heat transfer will not begin or continue. A pair of check valves are coupled in the loop, and the heater is cycled for augmentation pumping of coolant to and from the reservoir. This augmentation pumping, in conjunction with the check valves, wets the wick. The wick liquid storage capacity allows the augmentation pump to provide continuous pulsed liquid flow to assure continuous vapor transport and a continuously operating heat transport system. The check valves are of the ball type to assure maximum reliability. However, any type of check valve can be used, including designs which are preloaded in the closed position. The check valve may use any ball or poppet material which resists corrosion. For optimum performance during testing on Earth, the ball or poppet would have neutral buoyancy or be configured in a closed position when the heat transport system is not operating. The ball may be porous to allow passage of coolant vapor.
    Keywords: Fluid Mechanics and Thermodynamics
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    Controlling the Mobility of the Fluid Interface of Moving Gas Bubbles or Liquid Drops by Using Micellar Solutions of Surfactants (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Microgravity processes must rely on mechanisms other than buoyancy to move bubbles or droplets from one region to another in a continuous liquid phase. One suggested method is thermocapillary migration in which a temperature gradient is applied to the continuous phase. A significant and as yet unresolved impediment to the use of thermocapillary migration to direct bubble or drop motion is that these migrations can be significantly retarded by the adsorption onto the fluid particle surface of surface active impurities unavoidably present in the continuous or (if the particle is a liquid) droplet phases. The focus of our research was to develop a theory for remobilizing fluid particle interfaces retarded by a surfactant impurity in an effort to make more viable the use of thermocapillary migrations for the management of bubbles and drops in microgravity. We postulated that a surfactant at high bulk concentration which kinetically exchanges rapidly with the surface can restore interface mobility. The scaling arguments along with a discussion of the previous literature is reviewed in the context of the scaling framework. The specific objectives of the research were twofold. The first was to prove the remobilization theory by studying a model problem. As the mechanism for remobilization is independent of the force which drives the particle, the fluid particle shape and the presence of fluid inertia, we chose the simplest model consisting of a spherical bubble rising steadily by buoyancy in creeping flow. We solved the hydrodynamic and surfactant transport equations for rapid kinetic exchange to demonstrate that as the concentration increases, the Marangoni retardation at first increases (the low k behavior) and then decreases (the high k behavior). The second objective was to develop a method to determine the kinetic rate constants of a surfactant molecule, since this information is necessary to select surfactants which will exchange rapidly enough relative to the convective rate in the thermocapillary process of interest. To measure the kinetic rate, we measure the dynamic tension change accompanying adsorption onto an initially clean interface, or the re-equilibration in tension when an equilibrium interface is compressed. The dynamic tension measurements are made by a pendant bubble method, in which surfactant adsorbs onto a pendant bubble, and the tension is measured by analyzing the shape change in the bubble. We conclude this report by detailing the publications, presentations and doctoral thesis completed under the auspices of this grant.
    Keywords: Fluid Mechanics and Thermodynamics
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    Parallel Domain Decomposition Preconditioning for Computational Fluid Dynamics (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This viewgraph presentation gives an overview of the parallel domain decomposition preconditioning for computational fluid dynamics. Details are given on some difficult fluid flow problems, stabilized spatial discretizations, and Newton's method for solving the discretized flow equations. Schur complement domain decomposition is described through basic formulation, simplifying strategies (including iterative subdomain and Schur complement solves, matrix element dropping, localized Schur complement computation, and supersparse computations), and performance evaluation.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: VecPar ''98; Jun 21, 1998 - Jun 23, 1998; Porto; Portugal
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    Computational Analysis of Shock Layer Emission Measurements in an Arc-Jet Facility (1998)
    In:  Other Sources
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    Publication Date: 2019-07-19
    Description: This paper reports computational analysis of radiation emission experiments in a high enthalpy arc-jet wind tunnel at NASA Ames Research Center. Recently, as part of ongoing arc-jet characterization work, spectroscopic radiation emission experiments have been conducted at the 20 MW NASA Ames arc-jet facility. The emission measurements were obtained from the arc-jet freestream and from a shock layer formed in front of flatfaced models. Analysis of these data is expected to provide valuable information about the thermodynamic state of the gas in the arc-jet freestream and in the shock layer as well as thermochemical equilibration processes behind the shock in arc-jet flows. Knowledge of the thermodynamic state of the gas in arc-jet test flows and especially within the shock layer is essential to interpret the heat transfer measurements such as in surface catalysis experiments. The present work is a continuation of previous work and focuses on analysis of the emission data obtained at relatively low-pressure conditions for which the arc-jet shock layer is expected to be in thermal and chemical nonequilibrium. Building blocks of the present computational analysis are: (1) simulation of nonequilibrium expanding flow in the converging-diverging conical nozzle and supersonic jet; (2) simulation of nonequilibrium shock layer formed in front of the flat-faced cylinder model; and (3) prediction of line-of-sight radiation from the computed flowfield. For computations of the nonequilibrium flow in the conical nozzle and shock layer, multi-temperature nonequilibrium codes with the axisymmetric formulation are used. For computations of line-of-sight radiation. a nonequilibrium radiation code (NEQAIR) is used to predict emission spectra from the computed flowfield. Computed line-of-sight averaged flow properties such as vibrational and rotational temperatures, species number densities within the shock layer will be compared with those deduced from the experimental spectra. Detailed comparisons of computational and experimental spectra will also be presented.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: 36th AIAA Aerospace Sciences Meeting and Exhibit; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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    Arcjet Semi-Elliptic Nozzle Simulations and Validation in Support of TPS Testing (1998)
    In:  Other Sources
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    Publication Date: 2019-07-19
    Description: Much of the ground based testing of advanced thermal protection system (TPS) components for the X33 program is done in arc-heated wind tunnels such as those located in the Arc-Jet Complex at NASA Ames Research Center. These facilities are capable of simulating the high temperature, chemically reacting flow environment experienced by the vehicle during flight. This allows one to test critical design issues such as maximum reuse temperatures, seals, gaps, and increases in heating due to interfaces between different materials. Computational fluid dynamics (CFD) has evolved to the point where it now can be used in the vehicle design process for accurate and timely prediction of trajectory based aerothermal heating environments for re-entry vehicles. It can also be used for simulation of the flow environments in ground based facilities such as arcjets. By utilization of the same CFD code and solution methodology, the important differences between ground test and flight may be quantified. The goal of this paper is to utilize CFD to provide validated simulations of the flow environment in the NASA-Ames semi elliptic nozzle arcjet facilities. The validation of the ground simulations will come From comparison to existing calibration data. Specific tests in support of the X33 TPS test program will ilso be simulated. In this manner, the differences between the ground test simulation and the flight environment can be identified for a measure of ground test to flight traceability.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: 36th AIAA Aerospace Sciences Meeting and Exhibit; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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    Advanced Subsonic Combustion Rig (1998)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: Researchers from the NASA Lewis Research Center have obtained the first combustion/emissions data under extreme future engine operating conditions. In Lewis' new world-class 60-atm combustor research facility--the Advanced Subsonic Combustion Rig (ASCR)--a flametube was used to conduct combustion experiments in environments as extreme as 900 psia and 3400 F. The greatest challenge for combustion researchers is the uncertainty of the effects of pressure on the formation of nitrogen oxides (NOx). Consequently, U.S. engine manufacturers are using these data to guide their future combustor designs. The flametube's metal housing has an inside diameter of 12 in. and a length of 10.5 in. The flametube can be used with a variety of different flow paths. Each flow path is lined with a high-temperature, castable refractory material (alumina) to minimize heat loss. Upstream of the flametube is the injector section, which has an inside diameter of 13 in. and a length of 0.5-in. It was designed to provide for quick changeovers. This flametube is being used to provide all U.S. engine manufacturers early assessments of advanced combustion concepts at full power conditions prior to engine production. To date, seven concepts from engine manufacturers have been evaluated and improved. This collaborated development can potentially give U.S. engine manufacturers the competitive advantage of being first in the market with advanced low-emission technologies.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 1997; NASA/TM-1998-206312
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    Electronic Resource
    Electronic Resource
    Über neue Reaktionsprodukte des Diacetyls mit Äthylendiamin und PolyaminenHerrn Professor Dr. B. Helferich zum 65. Geburtstage gewidmet. (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 69-74 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Umsetzung von 2 Moll. Athylendiamin mit 1 Mol. Diacetyl wurde eine neue bicyclische Verbindung erhalten. Das dieser Verbindung zugrunde liegende Ringsystem wird als Naphthpiperazin bezeichnet. Ein sich hiervon ableitendes tricyclisches Ringsystem wurde durch Kondensation von Diacetyl mit N.N′-Bis-[2-amino-äthyl]-1.3-diamino-propan erhalten. In analoger Weise ergab die Kondensation von N.N′-Bis-[2-amino-phenyl]-1.3-diamino-propan eine pentacylische Verbindung.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860113
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    Electronic Resource
    Electronic Resource
    Imidazolsynthesen mit Formamid (Formamid-Reaktionen, I. Mitteil.) (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 88-96 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus α-Oxy-, α-Halogen-, α-Amino- und unter reduzierenden Bedingungen auch aus α-Isonitroso-ketonen entstehen mit Formamid 4.5-substituierte Imidazole. Formamid dient im Überschuß gleichzeitig als Lösungsmittel.
    Additional Material: 3 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860117
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    Electronic Resource
    Electronic Resource
    Notiz zur Synthese des Xanthopterins (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 114-116 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die von F. Korte beschriebene Xanthopterin-Synthese gelingt nur bei Verwendung einer Dichloressigsäure, die im Anschluß an ihre Darstellung noch einer besonderen Reinigung unterworfen wird. Das Mißlingen der Synthese bei Anwendung der nicht gereinigten Säure ist auf die Gegenwart geringer Mengen Blausäure und weiterer esterartig riechender Verunreinigungen zurückzuführen. Es wird ein einfaches Reinigungsverfahren für die Dichloressigsäure beschrieben, nach dessen Durchführung die Xanthopterin-Synthese mit Ausbeuten von über 45% glatt reproduzierbar ist.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860121
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  • 61
    Electronic Resource
    Electronic Resource
    1-Acetyl-2.3.5-tribenzoyl-d-ribose aus Guanosin (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 160-161 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus Guanosin läßt sich über die 2′.3′.5′-Tribenzoyl-Verbindung durch Hydrolyse unter geeigneten Bedingungen und Acetylierung der entstandenen 2.3.5-Tribenzoyl-d-ribose die 1-Acetyl-2.3.5-tribenzoyl-d-ribose in etwa 50-proz. Ausbeute gewinnen.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860206
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  • 62
    Electronic Resource
    Electronic Resource
    Studien über den Mechanismus chemischer Reaktionen, XIII. Mitteil.XII. Mitteil.: K. Kindler, E. Schärfe u. P. Henrich: Über die Abstimmung von Palladium durch minimale Mengen von Säuren und Basen bei Hydrierungen aliphatisch-aromatischer Ketone, Liebigs Ann. Chem. 565, 51 [1949].: Spezifische Hydrierungen von Halogen-allyl-phenolen zu Halogen-propyl-phenolen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 167-172 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Während bei der Hydrierung von 4-Chlor- bzw. von 4-Brom-2-allyl-phenolen in sauerstoffhaltigen Lösungsmitteln, wie Alkohol und Eisessig, außer der Absättigung des Allylrestes stets eine teilweise Abspaltung des Halogens als Halogenwasserstoff eintritt, wird in Kohlenwasserstoffen nur die Allylgruppe abgesättigt. Ähnlich spezifisch verläuft die Hydrierung auch in alkoholischer Lösung, wenn sie unter Zusatz von minimalen Mengen Nicotinsäureamid, Nicotinsäurediäthylamid oder Thiophen durchgeführt wird. Von den leicht zugänglich gemachten Halogen-propyl-phenolen zeigen einige eine ungewöhnlich starke baktericide Wirkung.
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    URL: http://dx.doi.org/10.1002/cber.19530860208
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    Einwirkung von Schwefel auf α-Picolin (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 205-207 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Einwirkung von Schwefel auf α-Picolin wird eine Base C36H24N6S2 gewonnen, die durch Reduktion zu einer Base C18H13N3 abgebaut wird. Beide Stoffe lassen sich in das gleiche Nitro-Produkt C18H12N3·NO2 überführen. Für die Verbindungen werden Konstitutionsformeln vorgeschlagen.
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    URL: http://dx.doi.org/10.1002/cber.19530860214
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    Ein neues Prinzip zur Darstellung höhergliedriger Ringsysteme, I. Mitteil.: Ringschluß-Reaktionen bei Sulfonamiden des o-Phenylendiamins (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 197-205 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird ein neues Prinzip zur Darstellung höhergliedriger Ringsysteme beschrieben. Es beruht darauf, daß man von solchen offenkettigen Verbindungen ausgeht, bei denen eine Reaktion zwischen mehreren Molekülen, die zu Polykondensaten führt, aus sterischen Gründen unmöglich ist, während die Ringschluß-Reaktion sterisch nicht behindert ist. Verbindungen, bei welchen diese sterischen Voraussetzungen erfüllt sind, wurden in den Sulfonamiden des o-Phenylendiamins gefunden. Durch Kondensation mit α.ω-Dihalogen-Verhindungen konnten 7-, 8-, 9- und 10-gliedrige Ringe ohne Anwendung des Verdünnungsprinzips dargestellt werden.
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    URL: http://dx.doi.org/10.1002/cber.19530860213
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    Über den Abbau des Kakothelins mit alkalischem Wasserstoffperoxyd, insbesondere über die Säure C20H23O8N3 (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 232-261 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Kakothelin wird durch alkalisches Wasserstoffperoxyd unter Öffnung des Chinonrings und Decarboxylierung zum Aminoxyd C20H23O9N3 abgebaut, das sich zu C20H23O8N3 reduzieren läßt. Die Struktur dieser sauren Aminosäure als Glycidsäure mit einer Nitromethylen-Gruppe wird unter anderem durch das Verhalten bei der Reduktion bewiesen. Mit verd. Jodwasserstoffsäure entsteht die Oxysäure C20H25O8N3, mit Eisen (II)-hydroxyd das Oxim C20H23O7N3.Als Nebenprodukte des Abbaus werden durch Phenol-Extraktion der mit Schwefeldioxyd behandelten Mutterlauge die unbekannten Säuren C19H22O7N2 und die Sulfonsäure C20H24O9N2S gewonnen. Die C19-Verbindung dürfte ein Epoxyd der Hanssen-Säure sein. Ferner wurde eine Säure C20H24O7N2 isoliert. Unter geeigneten Bedingungen scheint der Abbau bis zur C18-Stufe zu führen.
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    Zur spektroskopischen Identifizierung des Stammkohlenwasserstoffes mehrkerniger Oxy-chinone (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 432-443 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch acetylierende Reduktion von Oxy-anthrachinonen wurden vierzehn Acetoxy-anthracene dargestellt. Aus ihren UV-Absorptionskurven ergibt sich, daß Acetoxygruppen im Anthracen bathochrom wirken, die typische Gestalt der Anthracen-Kurve aber nicht wesentlich verändern. Infolgedessen besteht die Möglichkeit, bei Oxy-chinonen unbekannter Konstitution durch acetylierende Reduktion und spektroskopische Untersuchung des Reduktionsproduktes festzustellen, ob der Stammkohlenwasserstoff Anthracen ist.
    Additional Material: 4 Ill.
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    URL: http://dx.doi.org/10.1002/cber.19530860320
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    Masthead (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953) 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860401
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    Zur Strukturspezifität des Vitamins B1, VIII. MitteilungI. Mitteil.: Ber. dtsch. chem. Ges. 73, 44 [1940]; II. Mitteil. ebenda 73, 156 [1940]; III. Mitteil.: ebenda 73, 353 [1940]; IV. Mitteil.: ebenda 74, 442 [1942]; V. Mitteil.: Chem. Ber. 80, 502 [1947]; VI. Mitteil.: ebenda 80, 505 [1947]; VII. Mitteil.: ebenda 82, 117 [1949]. (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 461-465 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es werden einige Vitamin B1 Analoga und deren Antagonisten beschrieben.
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    URL: http://dx.doi.org/10.1002/cber.19530860402
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    Darstellung der Zuckertetrazolium-Verbindungen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 472-476 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus dem d-Galakto-diphenyl-formazan-pentaacetat wurde durch Oxydation mit Bleitetraacetat das d-Galakto-diphenyl-tetrazoliumchlorid-pentaacetat dargestellt und aus diesem das d-Galakto-diphenyl-tetrazoliumchlorid.
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    URL: http://dx.doi.org/10.1002/cber.19530860405
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    Über 1.2-Dialkoxy-äthene, I. Mitteil.: Darstellung und Charakterisierung von 1.2-Diäthoxy-äthen und 1.2-Dipropoxy-äthen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 148-154 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Darstellung von 1.2-Diäthoxy-äthen durch katalytische Alkohol-Abspaltung aus Äthoxyacetaldehyd-diäthylacetal mit Hilfe von Silicagel und sek. Natriumphosphat und die Darstellung von 1.2-Dipropoxy-äthen aus Propoxyacetaldehyd-dipropylacetal in Gegenwart von Cerdioxyd werden beschrieben.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/cber.19530860204
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    Über einen Fall von sterischer Hinderung bei der Alkylierung von Sulfonamiden aromatischer Diamine (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 161-167 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei Alkylierungen von N.N′-Ditosyl-o-phenylendiamin wurde gefunden, daß für die Einführung von 2 Alkylresten eine sterische Hinderung auftritt, wenn die Raumerfüllung der Alkylreste eine bestimmte Größe überschreitet. Die Reste Methyl, Äthyl und Allyl lassen sich 2 mal in das Molekül einführen, während räumlich größere Reste nur noch einmal einzutreten vermögen. Ähnliche Verhältnisse wurden bei der Alkylierung von N.N′-Ditosyl-naphthylendiamin-(2.3) gefunden. Die Alkylierung von N.N′-Ditosyl-naphthylendiamin-(1.8) ergibt infolge der größeren räumlichen Nachbarschaft der beiden N-Atome ausschließlich Monoalkylierungsprodukte.
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    Über Triazine, IV. Mitteil.III. Mitteil.: Ch. Grundmann, G. Weisse u. S. Seide, Liebigs Ann. Chem. 577, 77 [1952].: Phenyltriazin (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 181-186 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 2-Phenyl-1.3.5-triazin wurde auf zwei verschiedenen Wegen dargestellt. Dichlorphenyltriazin wurde in Bis-methylmercapto-phenyltriazin übergeführt und dieses mit Raney-Nickel reduktiv entschwefelt. Bis-trichlormethyl-phenyltriazin wurde zum Dimethyl-phenyl-triazin reduziert und dieses zur Phenyl-triazin-dicarbonsäure oxydiert, die bei thermischer Decarboxylierung ebenfalls Phenyltriazin liefert.
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    URL: http://dx.doi.org/10.1002/cber.19530860210
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    Die Einwirkung von Schwefel auf ein Gemisch von α-Picolin mit aromatischen Nitro-Verbindungen oder Aminen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 208-213 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Wird ein Gemisch von α-Picolin und aromatischen Nitro- oder Nitroso-Verbindungen oder Aminen mit Schwefel gekocht, so entstehen nach einer neuen Reaktion die noch unbekannten Thiopicolinsäure-amide, in manchen Fällen zugleich auch 2-[α-Pyridyl]-benzthiazole.
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    Die Molekülschwingungs-Spektren des Naphthalins und seiner Derivate, I. Mitteil.: Darstellung deuterierter Naphthaline und ihre Raman-Spektren (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 214-226 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird die Darstellung des Oktadeutero-naphthalins und des Hexadeutero-benzols sowie von partiell deuterierten Naphthalinen beschrieben; die Raman-Spektren dieser Verbindungen werden angegeben.
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    Rhodomycin, II. Mitteil.I. Mitteil.: H. Brockmann, K. Bauer u. I. Borchers, Chem. Ber. 84, 700 [1951]. Ein von G. Shockman u. S. A. Waksman (Antibiotics and Chemotherapy 1, 68 [1951]) isoliertes amorphes, rotes Antibioticum, das mit unserem Rhodomycin sicher nicht identisch ist, erhielt zunächst den Namen Rhodomycin, wurde von den amerikanischen Autoren aber in dankenswerter Weise in Rhodomycetin umbenannt, als sie von unserer ersten Veröffentlichung Kenntnis erhielten. (Antibiotica aus Actinomyceten, X. Mitteil.IX. Mitteil.: H. Brockmann, H. Genth u. R. Strufe, Chem. Ber. 85, 426 [1952].) (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 261-269 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die beiden durch Gegenstromverteilung von Rhodomycin-Konzentraten erhaltenen Fraktionen A und B wurden durch nochmalige Gegenstromverteilung weitergereinigt. Aus der Fraktion A wurde kristallisiertes Rhodomycin-hydrochlorid gewonnen.
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    Über β- und γ-Keto-sulfonium-Salze und ihren Zerfall in wäßriger Lösung (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 443-450 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: β-Keto-sulfonium-Salze zerfallen in wäßriger Lösung beim Erhitzen mit 1 Äquivalent Alkali unter Abspaltung von Wasser und intramolekularer Umlagerung; mit überschüssigem Alkali beobachtet man die hydrolytische Spaltung einer C—C-Bindung und Bildung von Carbonsäure neben Methyl-dialkyl-sulfonium-hydroxyd. γ-Keto-sulfonium-Salze spalten sich in wäßriger Lösung in Dialkylsulfide und Alkyl- bzw. Aryl-vinyl-ketone. Die Stabilität der untersuchten Sulfonium-Verbindungen ist verschieden, je nachdem ob an der Carbonyl-Gruppe ein aliphatischer oder aromatischer Rest gebunden ist.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/cber.19530860321
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    Reindarstellung von α-Methyl-N-acetyl-d-glucosaminid (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 466-467 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Das in der Literatur beschriebene Glucosid ([α]D: + 105°) ist ein Gemisch der α- und β-Form. Die reine α-Form ([α]D: + 131°) läßt sich über die Triacetyl-Verbindung gewinnen.
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    2-Acetonyl-thiazolin (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 468-472 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus 2-Methyl-thiazolin und Keten wird 2-Acetonyl-thiazolin erhalten, das mit Kupfersalzen eine Komplex-Verbindung liefert und im Rattenschwanz-Test blutdrucksenkend wirkt.
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    Herstellung und Konstitution zweier Ditrityltriacetylfructosen (Untersuchungen über Fructose-acetate, I. Mitteil.) (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 476-483 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Acetylierung mit Pyridin und Essigsäureanhydrid entsteht aus 1.6-Ditrityl-fructose Keto-1.6-ditrityl-3.4.5-triacetyl-fructose, mit Essigsäureanhydrid und Natriumacetat bildet sich 1.6-Ditrityl-2.3.4-triacetyl-fructofuranose. Die Konstitution der erstgenannten Verbindung wurde durch Darstellung des Ditrityltriacetylfructose-diäthyl-mercaptals sowie des Ditrityl-triacetyl- und Ditrityl-tetraacetyl-fructoseoxims bewiesen.
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    URL: http://dx.doi.org/10.1002/cber.19530860406
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    Studien über den Mechanismus chemischer Reaktionen, XIV. Mitteil.XIII. Mitteil.: K. Kindler, H. Oelschläger u. P. Henrich, Chem. Ber. 86, 167 [1953].: Spezifische Hydrierungen von 4-Halogen-2-acyl-phenolen zu 4-Halogen-2-alkyl-phenolen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 501-507 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Baktericid wirkende 4-Fluor- und 4-Chlor-2-alkyl-phenole mit einer unverzweigten Kohlenstoffkette werden durch spezifische Hydrierungen der entsprechenden Halogen-acyl-phenole leicht zugänglich gemacht. Bei den Chlor- Verbindungen gelingt dies durch Verwendung von Schwefelsäure als auswählendem Aktivator.
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    Notiz über die Isolierung der wasserlöslichen Aldosemercaptale mit Hilfe von IonenaustauschernAuszug aus der Habilitationsschrift von H. Zinner, eingereicht an der Mathematisch-Naturwissenschaftlichen Fakultät der Universität Jena (1952). (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 495-496 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus dem bei der Darstellung der wasserlöslichen Aldosemercaptale erhaltenen Gemisch von Mercaptal und Salzsäure wird die Säure mit Ionenaustauschern entfernt und das Mercaptal durch Eindampfen des Filtrats rein erhalten.
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    Über die stereoisomeren Hexahydro-anthranilsäuren (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 518-522 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es werden Synthesen, Eigenschaften und ein Konfigurationsbeweis für die stereoisomeren Hexahydro-anthranilsäuren angegeben.
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    URL: http://dx.doi.org/10.1002/cber.19530860414
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    Über das 10.11- und 11.12-Benzo-fluoranthen im Steinkohlenteer-Pech (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 534-536 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus dem Steinkohlenteer-Pech wurden im Siedebereich von 470 bis 480° zwei weitere Kohlenwasserstoffe abgetrennt, die sich als 10.11- bzw. 11.12-Benzo-fluoranthen erwiesen.
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    Masthead (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953) 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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    URL: http://dx.doi.org/10.1002/cber.19530860501
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    Über pflanzliche Herzgifte, XXIII. Mitteil.: Die Konstitution des Adonitoxigenins (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 574-584 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Adonitoxigenin, das Aglykon des Adonitoxins, wurde als 19-Oxogitoxigenin erkannt. Nach Überführung der Aldehydgruppe in das Äthylenmercaptal konnte durch Reduktion mit Raney-Nickel Gitoxigenin erhalten werden. Ferner wurde durch Hydrierung der Doppelbindung im Lactonring und durch Wasserabspaltung aus den beiden Oxygruppen an C14 und C16 Dianhydro-dihydro-gitoxigenin gewonnen, das mit einem aus Gitoxigenin hergestellten Vergleichspräparat identisch war.
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    Eine Synthese der Phenol-β-d-glucuronsäure (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 601-604 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird eine Synthese von Phenol-β-d-glucuronid, ausgehend von d-Glucuron, über den 1-Brom-triacetyl-α-d-glucuronsäure-methylester, beschrieben.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860509
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    Über eine neue Säure des PhosphorsVorgetragen auf der Chemie-Dozenten-Tagung in Bonn, April 1950; vergl. Angew. Chem. 62, 338 [1950]. (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 563-572 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus Hydrolysaten von Phosphortribromid in Natriumhydrogencarbonat-Lösungen wurde das Natriumsalz einer Säure des Phosphors isoliert, deren durch Säure katalysierte Hydrolyse 2 Moll. Phosphorige Säure liefert und für die der Name „Diphosphorige Säure“ vorgeschlagen wird.Diphosphorige Säure (H4P2O5) bzw. ihr Natriumsalz kann durch Halogene quantitativ entweder zu Unterphosphorsäure (H4P2O6) oder zu Pyrophosphorsäure (H4P2O7) bzw. den Salzen dieser Säuren oxydiert werden.Von der Pyrophosphorigen Säure Amats, die ebenfalls die Zusammensetzung H4P2O5 hat, ist die neue Verbindung durch ihre Reaktionen scharf unterschieden.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860503
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    Synthese der d,l-Di-n-alkyl-essigsäuren mit 19 bis 23 C-Atomen. (VI. Mitteil. über isomere und homologe Reihen)Zum 70. Geburtstag von Prof. Karl Thomas, Max-Planck-Institut für Medizinische Chemie, Göttingen. (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 688-692 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Di-n-alkyl-essigsäuren C19H38O2 bis C23H46O2 wurden durch doppelte Malonester-Synthese dargestellt.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860605
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    Synthesen von α-Aminosäuren, IV. Mitteil.: β-Oxy-α-aminosäuren (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 713-717 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus den durch Umsetzung von Phenacetylamino-acetessigester mit aromatischen Säurechloriden erhältlichen Aroyl-phenacetyl-amino-acetessigester-Derivaten entstehen durch Abspaltung der Acetyl-Gruppe und Reduktion der Carbonylgruppe erythro-β-Oxy-α-aminosäuren.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860610
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  • 90
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    Methylglucosid-Bildung von N-Acyl-glucosaminen mit Diazomethan (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 724-730 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: N-Acetyl-glucosamin liefert mit überschüssigem Diazomethan 40% d. Th an krist. β-Methyl-N-acetyl-glucosaminid. Auch aus N-Formyl-und N-Carbobenzoxy-glucosamin wurden die entsprechenden β-Methylglucoside kristallisiert erhalten. Glucose reagiert unter den angegebenen Bedingungen unter Verlust des Reduktionsvermögens und Bildung von methoxylhaltigen Produkten, unter denen papier chromatographisch Methylglucosid nachgewiesen werden konnte.
    Additional Material: 3 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860613
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  • 91
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    d,l-Pinoresinol, ein weiteres Zwischenprodukt der Ligninbildung (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 755-758 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Unter den niedermolekularen Produkten der Dehydrierung, die der Coniferylkohol bei der Ligninbildung erleidet, wurde außer dem früher festgestellten Dehydro-diconiferylalkohol (I) das bisher unbekannte d,l-Pinoresinol (II) gefunden. Beide sind Bausteine des Lignins.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860619
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  • 92
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    Notiz über die Identifizierung der Aldosen als deren β-Phenyl-äthyl-mercaptale (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 781-784 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es werden die bisher unbekannten β-Phenyl-äthyl-mercaptale der Aldosen und ihre Additionsverbindungen mit Quecksilber (II)-chlorid dargestellt.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860624
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  • 93
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    Über α- und β-Sulfonyl-sulfonium-Salze (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 785-790 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: α-Sulfonyl-sulfonium-Salze lassen sich durch Oxydation von Alkylmercaptomethyl-sulfonium-Salzen mit Peressigsäure gewinnen; sie sind als Reineckate oder Methansulfonate beständig, zerfallen als Chloride hingegen in wäßriger Lösung unter Bildung von α-Mercaptosulfonen.β-Sulfonyl-sulfonium-Salze entstehen durch Anlagerung von Alkylhalogeniden an β-Sulfonyl-sulfide; sie sind in wäßriger Lösung beständig und zerfallen bei Gegenwart von Alkali wie die analogen γ-Keto-sulfonium-Salze in Dialkyl-sulfide und Alkyl- bzw. Aryl-vinyl-sulfone.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860625
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    Polyacetylene, IV. Mitteil.I. Mitteil.: F. Bohlmann, Angew. Chem. 63, 218 [1951]; II. Mitteil.: Chem. Ber. 84, 785 [1951]; III. Mitteil.: Chem. Ber. 85, 63 [1953].: Darstellung von Di-tert.-butyl-polyacetylenen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 657-667 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird die Darstellung von Di-tert.-butyl-acetylenen mit 2 bis 7 konjugierten Dreifachbindungen beschrieben. Gegenüber den bisher untersuchten Polyinen zeigt diese Reihe eine erheblich größere Beständigkeit. Es konnte daher erstmals auch eine Heptaacetylen-Verbindung dargestellt werden.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860519
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    Die Schmelzpunkte der isomeren und homologen Reihen der d,l-Oxyparaffine, Ketoparaffine und d,l-Paraffin-carbonsäuren (III. Mitteil. über isomere und homologe Reihen) (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 669-678 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Schmelzpunkts-Reihen der in den folgenden Mitteilungen IV, V und VI beschriebenen reinen isomeren n-d,l-Oxyparaffine, Ketoparaffine und d,l-Paraffincarbonsäuren mit Kettenlängen von 14 bis 23 C-Atomen werden graphisch dargestellt. Alle möglichen Isomeren einer Reihe ordnen sich ausnahmslos in regelmäßigen oder alternierenden Kurven an, die in allen Isomeren-Reihen analog verlaufen, und so Voraussagen über die Schmelzpunkte von noch unbekannten Paraffin-Derivaten erlauben. In einigen homologen Reihen der Oxy-paraffine tritt ein bisher unbekannter treppenförmiger Verlauf der Schmelzpunkte auf.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860602
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    Über Metallcarbonyle, LVIII. Mitteil.LVII. Mitteil.: R. Nast u. H. Roos, Z. anorg. allg. Chem. 1953 (im Druck).: Über die Reaktion des Kobalt-tetracarbonyls mit verschiedenartigen Basen (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 700-710 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Reaktion von Kobaltcarbonyl mit Aminen und Alkoholen, d. h. mit N- bzw. O-Basen, besteht in einer Valenzdisproportionierung des Carbonylmetalls: 3 Co° → Co⊕⊖ + 2 Co⊖. Sie führt unter Abgabe von CO zur Bildung komplexer Kobalt(II)-di-kobaltcarbonylate, deren Kation die entsprechende Base als Ligand enthält. Die schon lange bekannte Reaktion des dimeren Carbonyls mit wäßrigem Ammoniak: 3 [Co(CO)4]2 + 12 NH3 → 2 [Co(NH3)6] [Co(CO)4]2 + 8 CO erweist sich als der Prototyp dieser Umsetzungen.Zum Unterschied von der früheren Auffassung, wonach bei der Einwirkung von Aminen und Alkoholen substituierte Carbonyl-Derivate entstehen sollen, handelt es sich tatsächlich um die Bildung ionogen gebauter CO-Komplexe; die damals mit 3 bzw. 2.5 CO/Co beschriebenen Verbindungen enthalten nämlich 2.67 CO/Co.In Gegenwart von OH⊖-Ionen reagiert das bei obiger Reaktion freiwerdende CO mit noch vorhandenem Carbonyl unter Bildung von Carbonat und Carbonylat, so daß bis zu 1.80 g-Ion [Co(CO)4]⊖/ [Co(CO)4]2 entstehen.Somit wird bei den Reaktionen des dimeren Kobalt-tetracarbonyls stets die maximal mögliche Menge [Co(CO)4]⊖ gebildet.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860608
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    Über die β-Form des N-Acetyl-glucosamins (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 722-724 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: In Dimethylformamid bei tiefer Temperatur läßt sich β-d-Glucosamin mit Essigsäureanhydrid unter Erhaltung der β-Konfiguration N-acetylieren. In entsprechender Weise wurde die β-Form des N-Propionyl-d-glucosamins gewonnen.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860612
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    Notiz über Cyclohexandion-(2.5)-diessigsäure-(1.4)Auszug aus der Diplomarbeit G. Fritz, Freiburg i. Br. 1951. (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 737-740 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird ein Verfahren zur Darstellung der Cyclohexan-dion-(2.5)-diessigsäure-(1.4), die in zwei isomeren Formen isoliert werden konnte beschrieben.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860616
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    Die Konstitution der Dimethylen-glucose Lobry de Bruyns und der Monomethylen-glucose von Tollens (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 741-749 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Dimethylen-glucose wurde kristallisiert erhalten. Ihre Konstitution entspricht derjenigen der Isodiaceton-glucose; die 6-Stellung ist unbesetzt, was u.a. aus der Umwandlung in eine Dimethylen-glucuronsäure hervorgeht. Die 6-Acetyl-dimethylen-glucose wird durch Kaliumpermanganat in phosphorsaurer Lösung zum 6-Acetylmonomethylen-glucose-carbonat-(1.2) oxydiert, aus dem eine Monomethylen-glucose erhalten wird, die Fehlingsche Lösung reduziert und ein Monomethylen glucose-phenylosazon liefert. In ihr ist die Methylengruppe in 3.5-Stellung gebunden, da sie nur 1 Mol. Natriumperjodat verbraucht. Die zweite Methylengruppe der Dimethylen-glucose sitzt in 1.2-Stellung.Für die Monomethylen-glucose von Tollens wird ein neues einfacheres Darstellungsverfahren angegeben. Sie enthält die Methylen-gruppe in 4.6-Stellung, wie sich aus dem Verbrauch von 2 Moll. Perjodat unter Bildung von 2 Moll. Ameisensäure ergibt.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860617
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    Über Thiazole, XV. Mitteil.XIV. Mitteil.: Arch. Pharmaz., Ber. dtsch. pharmaz. Ges. 286, 13, [1953]; vergl. G. Ruhlig, Diplomarbeit, Greifswalf 1953.: Über die Kondensation von Chloraceton mit Thiosemicarbazid und einige Umlagerungen in der Thiazolreihe (1953)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 86 (1953), S. 764-769 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Kondensation von Chloraceton mit Thiosemicarbazid führt in absolut alkoholischer Lösung über S-Acetonyl-isothiosemicarbazid als faßbarem Zwischenprodukt zum 3-Amino-4-methyl-thiazolon-(2)-imid, das andererseits durch Umsetzung von Chloraceton mit Thiosemicarbazid-hydrochlorid in fast quantitativer Ausbeute erhalten wird. Es geht mit Salpetriger Säure in [4-Methyl-thiazolo-(2.3)]-tetrazol über, das auf die gleiche Weise aus 4-Methyl-thiazolyl-(2)-hydrazin erhältlich ist.Unter bestimmten Reaktionsbedingungen läßt sich 3-Amino-4-methyl-thiazolon-(2)-imid sowohl in 2-Amino-5-methyl-1.3.4-thiodiazin als auch in 4-Methyl-thiazolyl-(2)-hydrazin intramolekular umlagern. Diese Umlagerungen verlaufen offenbar über S-Acetonyl-isothiosemicarbazid, da auch dieses durch Wasserabspaltung in die drei soeben genannten Verbindungen überführbar ist.Die Konstitution des S-Acetonyl-isothiosemicarbazids konnte auf synthetischem Wege gesichert werden.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19530860621
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